From Summary: "An application of airfoil design methods was used to design series of related turbine-blade profiles to satisfy the conditions of inlet flow angle and turning angle encountered in the usual range of turbine operation. A series of blade profiles applicable to most turbine blading requirements and a secondary series with particular reference to impulse conditions were designed. Five blade sections from these series ranging in mean-line turning angles from 63 deg. to 120 deg. were tested in low-speed cascade tunnels."

Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.

Memorandum presenting testing of an experimental Custer Channel Wing airplane in the full-scale tunnel to investigate the lift characteristics of a channel-propeller combination and the flow phenomena in and about a channel wing.

Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.

Report presenting an investigation of three NACA 1-series nose inlets at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements and schileren photographs were obtained at zero angle of attack through a range of Mach numbers and mass-flow-ratios. Results regarding tunnel boundary interference, surface pressure distribution, external drag, and pressure recovery are provided.

Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.

From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."

Memorandum presenting an investigation of the leading-edge extensions, a trailing-edge extension, and a fence on the static longitudinal stability of a wing-fuselage-tail combination with a wing with 35 degrees of sweepback and an aspect ratio of 4.5. The investigation involved the use of force measurements and tuft studies on stall progression. Results regarding a model with unmodified wing, the effect of leading-edge modifications, the effects of the fence, a summary of the effects of compressibility, and some remarks on flow separation are provided.

"An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having various fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 10(exp 6) to 10 x 10(exp 6). The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number" (p. 1).

Report presenting a theoretical study of certain anomalies in the behavior of a ram-jet engine engine tip-mounted on a rotating helicopter blade that appears to be related to centrifugal effects distorting the fuel-spray pattern. Results regarding the cases calculated, results of the calculations, particle-path distortion, and limiting direction of particle paths are provided.

Report presenting an experimental wing-flutter investigation in the transonic blowdown tunnel, which is equipped with a slotted test section, in order to determine the correlation between transonic-wind-tunnel and free-fall flight flutter results. Very good agreement was observed between wind tunnel and flight flutter test results, which showed the feasibility of conducting flutter tests in transonic wind tunnels with slotted test sections.

Memorandum presenting an inlet-type axial-flow compressor rotor with a hub-tip diameter ratio of 0.4 at the rotor leading edge, which was designed, fabricated, and experimentally investigated. The results of the investigation indicated that stages with inlet hub-tip ratios as low as 0.4 can be designed within known practical aerodynamic specifications to produce satisfactory values of stage pressure ratio and efficiency at high specific weight flows.

Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.

Report presenting an investigation of an ogive-cylinder nacelle in various spanwise locations in a vertically symmetric position on a small-size 45 degree sweptback wing of aspect ratio 6 with and without a fuselage. Results regarding the drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.

Report presenting an investigation of the power requirements for slotted tunnels and methods of reducing these requirements. All pressure losses reported occurred in the region between the upstream end of the entrance ball and the entrance to the diffuser and in handling air taken in through the slotted wall. Results regarding auxiliary pumping and ejector pumping are provided.

Memorandum presenting an investigation of operation of a single-spool turbojet engine with variable exhaust-nozzle area over a range of altitudes at a constant flight Mach number. Data was obtained by subjecting the engine to approximate step disturbances in the independent variables, and the information necessary to effect a linearized first-order description of the engine's dynamic operation was obtained. Results regarding rotational speed, compressor-discharge pressure, turbine-discharge pressure, net thrust, and turbine-discharge temperature are provided.

Report presents an investigation to determine the transonic aerodynamic characteristics of W-plan-form wing of aspect ratio 3.5, taper ratio 0.25, and 60 degree 48 minute panel sweep by using a small reflection plane over which high subsonic and low subsonic Mach numbers are obtained. Comparisons are made between sweptback-wing data to determine the effectiveness of the W-plan modifications.

Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.

None

The usefulness of the Ewing equation for calculating the thermal conductivity of reactor metals and alloys from electrical resistance, specific heat, density, and atomic weight was investigated. The alloys investigated were Zircaloy-2, HSZA, Nb- 5.5 wt% V, Inconel, 18-8 stainless steel, and eutectic NaK. The Ewing equation was found to give calculated values with a degree of confidence similar to that of actual measured values. (auth)

Report covering an experiment on a method for determining the crystallographic orientation within uranium rods. From summary: "The crystallographic orientation existing in rolled uranium rods may be determined by comparing the diffraction pattern obtained from an unknown specimen with the diffraction pattern obtained from a sample known to be randomly oriented."

Abstract: "The heat of solution of thorium sesquisulfide was determined in 6.000 molar HCl at 25 C to ascertain the stability of the thorium (III) halides. The molal heat of formation of Th2S3 from rhombic sulfur and crystalline thorium is calculated as 258.6 kcal."

This is a preliminary report on a multigroup's analysis on the IBM 604, a programmable Electronic Calculating Punch, as part of the course work W31-Eng. 52.

Daily cash report for Imperial Sugar Company including a list of large withdrawals for the months surrounding the date showing the daily expenses and estimated balance for each entry. It also lists scheduled payments for bank loans.